XFOIL Version 6.96 Calculated polar for: NASA SC(2)-1010 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.9985 0.07933 0.07668 -0.0531 0.9999 0.0111 -18.500 -1.0471 0.06653 0.06367 -0.0609 0.9999 0.0110 -18.250 -1.0777 0.05730 0.05426 -0.0671 0.9999 0.0109 -18.000 -1.0969 0.05037 0.04719 -0.0720 0.9999 0.0110 -17.750 -1.1096 0.04486 0.04154 -0.0759 0.9999 0.0110 -17.500 -1.1165 0.04057 0.03713 -0.0787 0.9999 0.0111 -17.250 -1.1221 0.03702 0.03347 -0.0805 0.9999 0.0112 -17.000 -1.1302 0.03412 0.03048 -0.0808 0.9999 0.0112 -16.750 -1.1483 0.03191 0.02819 -0.0781 0.9999 0.0113 -16.500 -1.1436 0.02963 0.02581 -0.0794 0.9992 0.0114 -16.250 -1.1201 0.02741 0.02345 -0.0839 0.9975 0.0115 -16.000 -1.0933 0.02551 0.02142 -0.0883 0.9961 0.0117 -15.750 -1.0643 0.02394 0.01972 -0.0922 0.9950 0.0118 -15.500 -1.0345 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0.2293 0.5855 -1.250 0.6801 0.00956 0.00278 -0.1470 0.1723 0.5949 -1.000 0.7070 0.00991 0.00297 -0.1468 0.1302 0.6055 -0.750 0.7343 0.01019 0.00316 -0.1467 0.1010 0.6164 -0.500 0.7617 0.01045 0.00334 -0.1465 0.0811 0.6265 -0.250 0.7892 0.01067 0.00352 -0.1464 0.0676 0.6366 0.000 0.8166 0.01091 0.00371 -0.1462 0.0543 0.6469 0.250 0.8439 0.01114 0.00391 -0.1460 0.0463 0.6573 0.500 0.8713 0.01135 0.00412 -0.1458 0.0413 0.6666 0.750 0.8986 0.01157 0.00432 -0.1456 0.0377 0.6741 1.000 0.9258 0.01178 0.00454 -0.1453 0.0349 0.6811 1.250 0.9527 0.01203 0.00477 -0.1450 0.0318 0.6878 1.500 0.9798 0.01223 0.00499 -0.1448 0.0303 0.6937 1.750 1.0066 0.01246 0.00523 -0.1444 0.0285 0.7000 2.000 1.0331 0.01274 0.00549 -0.1440 0.0265 0.7058 2.250 1.0598 0.01297 0.00576 -0.1437 0.0254 0.7116 2.500 1.0862 0.01322 0.00602 -0.1433 0.0241 0.7180 2.750 1.1124 0.01350 0.00631 -0.1428 0.0226 0.7236 3.000 1.1382 0.01380 0.00662 -0.1423 0.0212 0.7294 3.250 1.1643 0.01407 0.00692 -0.1418 0.0203 0.7347 3.500 1.1900 0.01437 0.00724 -0.1413 0.0193 0.7394 3.750 1.2154 0.01469 0.00757 -0.1407 0.0184 0.7442 4.000 1.2403 0.01508 0.00797 -0.1400 0.0174 0.7493 4.250 1.2656 0.01540 0.00833 -0.1394 0.0170 0.7546 4.500 1.2905 0.01574 0.00872 -0.1387 0.0164 0.7601 4.750 1.3151 0.01610 0.00912 -0.1380 0.0158 0.7666 5.000 1.3394 0.01649 0.00953 -0.1372 0.0153 0.7722 5.250 1.3634 0.01690 0.00997 -0.1363 0.0148 0.7777 5.500 1.3868 0.01737 0.01047 -0.1354 0.0142 0.7828 5.750 1.4100 0.01785 0.01099 -0.1344 0.0138 0.7871 6.000 1.4333 0.01827 0.01147 -0.1335 0.0136 0.7910 6.250 1.4563 0.01872 0.01198 -0.1324 0.0133 0.7954 6.500 1.4788 0.01920 0.01251 -0.1313 0.0130 0.7999 6.750 1.5009 0.01969 0.01306 -0.1302 0.0127 0.8045 7.000 1.5226 0.02020 0.01363 -0.1290 0.0124 0.8096 7.250 1.5439 0.02074 0.01422 -0.1277 0.0122 0.8148 7.500 1.5647 0.02130 0.01482 -0.1264 0.0119 0.8192 7.750 1.5848 0.02190 0.01548 -0.1249 0.0117 0.8236 8.000 1.6039 0.02256 0.01621 -0.1233 0.0114 0.8283 8.250 1.6216 0.02335 0.01706 -0.1214 0.0112 0.8327 8.500 1.6378 0.02418 0.01798 -0.1193 0.0110 0.8366 8.750 1.6546 0.02485 0.01874 -0.1173 0.0109 0.8410 9.000 1.6704 0.02556 0.01953 -0.1152 0.0108 0.8456 9.250 1.6848 0.02630 0.02037 -0.1128 0.0107 0.8501 9.500 1.6973 0.02708 0.02125 -0.1101 0.0106 0.8554 9.750 1.7074 0.02791 0.02217 -0.1070 0.0105 0.8609 10.000 1.7183 0.02878 0.02314 -0.1042 0.0103 0.8655 10.250 1.7292 0.02967 0.02414 -0.1015 0.0102 0.8701 10.500 1.7391 0.03067 0.02523 -0.0987 0.0101 0.8747 10.750 1.7484 0.03172 0.02639 -0.0960 0.0099 0.8795 11.000 1.7571 0.03282 0.02759 -0.0933 0.0098 0.8852 11.500 1.7709 0.03535 0.03035 -0.0878 0.0096 0.8998 11.750 1.7766 0.03669 0.03184 -0.0851 0.0095 0.9142 12.000 1.7787 0.03811 0.03341 -0.0819 0.0094 1.0001 12.250 1.7825 0.03980 0.03520 -0.0795 0.0093 1.0001 12.500 1.7852 0.04165 0.03715 -0.0771 0.0093 1.0001 12.750 1.7867 0.04366 0.03927 -0.0748 0.0092 1.0001 13.000 1.7864 0.04591 0.04164 -0.0726 0.0091 1.0001 13.250 1.7849 0.04836 0.04420 -0.0707 0.0090 1.0001 13.500 1.7809 0.05120 0.04716 -0.0689 0.0090 1.0001 13.750 1.7749 0.05438 0.05047 -0.0674 0.0089 1.0001 14.000 1.7666 0.05798 0.05420 -0.0663 0.0088 1.0001 14.250 1.7554 0.06220 0.05856 -0.0657 0.0088 1.0001 14.500 1.7418 0.06708 0.06360 -0.0658 0.0087 1.0001 14.750 1.7250 0.07286 0.06953 -0.0669 0.0087 1.0001 15.000 1.7055 0.07962 0.07648 -0.0691 0.0087 1.0001 15.250 1.6814 0.08792 0.08497 -0.0729 0.0087 1.0001 15.500 1.6508 0.09828 0.09553 -0.0787 0.0087 1.0001 15.750 1.6113 0.11133 0.10883 -0.0866 0.0087 1.0001 16.000 1.5524 0.12951 0.12730 -0.0980 0.0088 1.0001